Stabilizers for jet-propelled vehicles



Jan. 24, 1961 R. B. KERSHNER 2,959,017 STABILIZERS FOR JET-PROPELLEDVEHICLES Filed March 19, 1948 2 Sheets-$heet 1 36 FIG. 3

INVEN TOR. RICHARD B. KERSH N ER BY Kg 6%;

I ATTORNEY Jan. 24, 1961 R. B. KERSHNER 2,969,017

STABILIZERS FOR JET-PROPELLED VEHICLES Filed March 19, 1948 2Sheets-Sheet 2 IN VEN TOR.

RICHARD B. KERSH N ER ATTORNEY STABILIZERS FOR JET-PROPELLED VEHICLESRichard B. Kershner, Silver Spring, Md., assignor to the United Statesof America as represented by the Secretary of the Navy Filed Mar. 19,1948, Ser. No. 15,867

6 Claims. (Cl. 10250) The present invention relates to stabilizers forjet-propelled vehicles. More specifically, it relates to stabilizingmeans wherein the jet impringes on a control surface mechanicallyconnected with the veicle, in such way that a restoring force isproduced whenever the vehicle deviates from its intended course.

An object of the invention is to provide a stabilizer for ajet-propelled vehicle which will tend automatically to return thevehicle to its course whenever deviations occur, that is, whenever themotion is not parallel to the longitudinal axis of the vehicle.

A specific object is to provide pivotally mounted vanes on the outsideof a jet-propelled vehicle, and mechanism connecting said vanes to othervanes, exposed to the jet, so that whenever the axis of the vehicle doesnot coincide with its direction of motion, the external vanes will bedeflected by the air stream and will cause a corresponding movement ofthe vanes that are exposed to the jet, in such direction that arestoring moment is applied to the vehicle.

While the invention in its broader aspect is suitable for anyjet-propelled vehicle, it is of particular utility in connection withbooster rockets, such as are employed for launching ram jets, forinstance.

Solely for illustrative purposes, and not by way of limitation, theinvention is disclosed herein as applied to rockets, and several formsat present preferred are shown in the accompanying drawing, wherein:

Fig. l is a diagrammatic elevation, partly broken away and in section,of the complete rocket, with the invention applied thereto;

Fig. 2 is a diagrammatic fragmentary longitudinal axial section througha rocket, on a much larger scale than Fig. l, and showing only the jetend thereof, with the invention applied;

Fig. 3 is a fragmentary detail section on a still larger scale, througha pivotal joint used in the device, in the plane 33 of Fig. 2;

Figs. 4 to 9 inclusive illustrate three of many possible arrangements ofthe jet-deflecting vanes, as follows:

Figs. 4 and 5 are sections respectively on the planes 4-4 and 55, thatis, planes at right angles to one another, showing a form wherein theshaft-and-vane structure is continuous across the rocket, each being cutaway suitably, to allow the other to pass through it, with the shaftcenter-lines at the same level;

Figs. 6 and 7 are similar sections on planes 66 and 7-7, showing thesame type of shaft-and-vane structure as that already embodied in Figs.1 and 2; and

Figs. 8 and 9 are corresponding views of a type wherein each vane hasits own separate shaft, these views being elevations as seen from planes8--8 and 99 respectively.

Jet-propelled missiles are of two general types: First, those that carryboth fuel and an oxygen source, and known as rockets; and second, thosethat carry only the fuel and depend on the surrounding atmosphere tosupply the oxygen for its combustion, for example,

2,969,017 Patented Jan. 24, 1961 ram-jets, or turbo-jets. The presentinvention is applicable to both types, but while it deals primarily withcontrolling the direction of flight of a rocket, it is probable that itschief fields of use may be the control of artillery rockets and of thoserockets that are used in launching ram-jets, without however, excludingits use on other rocket missiles. Inasmuch as a ram-jet is notselfstarting, but must be brought to a high speed before its jet actioncan begin, it is at present customary to provide rocket-type launchingdevices for such ram-jets, and these rockets often cause difficulty bydeviating from a rectilinear course, for various reasons, and therebygiving a false direction to the ram-jet missile. Large fixed fins areused to minimize these deviations. The present invention elminates theneed for large fixed fins by providing means to deflect the rocketdischarge blast upon deviation of the rocket from its intended course,thereby producing a reaction that tends to restore the rocket to thecorrect direction of flight.

Referring first to Fig. 1, there is shown a rocket 10 of a type that maybe used for launching a ram-jet. This has a nose 11 at its forward,closed end, and a jet-directing nozzle 12 at its rear, open end. In Fig.1

this nozzle 12 necessarily is shown on a relatively small scale andhence Fig. 2 also should be consulted, for de-. tails.

The nozzle 12, here illustrated as a venturi tube, is located at theexhaust end of the rocket 10 and is surrounded by a fairing13 which maybe attached to the rocket in any suitable way, as by the tapered fitting14 which provides a smooth joint, as shown. The nozzle 12 may include aflange 15 as shown in Fig. 2, welded thereto at 16, said nozzle beingsecured to the adjacent end portion 17 of the rocket by cap screws 18 orthe like, an asbestos gasket 19 being interposed, to provide a tight,heat-resistant joint.

Just beyond the discharge mouth of the nozzle 12 are provided twojet-deflecting vanes 20, 20, secured to a shaft 21, which is mounted atits ends in suitable antifriction bearings 22 carried in supports 23,which may be held in the fairing 13 in any suitable way, as by screws24. To assist in holding the end of shaft 21 away from the walls of thesupports 23, springs 25 may be mounted in bores 26 in the said shaft,and exert thrust against the balls 27.

A crank arm 28 is rigidly secured to each end of the shaft 21. This armmay have, at its forward end, a sleeve 29 in which is held a crank pin30. At its other end, each crank arm 28 may be bent radially outward asshown at 31 and may carry suitable counterweights 32, held in place bythe threaded stud 33 and the nut: 34. A protective shield 35, of funnelshape, may be provided, to protect the bearings 22 and associatedmechanism from the heat and corrosive action of the rocket-blast gases.This shield may be made in four segments, to facilitate assembling.

A set of external vanes 36, each mounted on a corresponding shaft 37, towhich it may be secured rigidly by a number of screws 38 or othersuitable means, serves to manipulate the internal vanes 20. This isaccomplished by a set of crank arms 39, each rigidly secured to theinner end portion of the corresponding shaft 37. The shafts 37 arejournalled in suitable anti-friction bearings 40, each held in a support41, said supports being secured by screws 42 to the ring 59, which iswelded or otherwise secured to the fairing 13. Inasmuch as, in Fig. 2,the two sets of shafts 37 are located at different levels, so thatshafts 21 will not interfere, the ring 59 may have two raised portions60 to accommodate the higher pair of shafts 37, as shown at the left ofFig. 1.

Each arm 39 has at its lower end a forked portion 43, constructed hereof two separate jaw elements 44, secured to the crank arm 39 by screws45, and spaced apart by a block 46 and such shims 47 as may benecessary, a bolt 48 and nut 49 holding the assembly firmly in itsadjusted position, so that the hardened and rounded inner surfaces 50 ofthe jaw elements 44 will just fit the crank pin 30 without lost motion,as shown in Figs. 2 and 3. It will be noted that the arm 39 is shownbent back and forth, to ,fit within the restricted space in which itmust operate.

At the upper end of each arm 39 is a counterweight 51, on which may bemounted a suitably threaded stud 52 to carry counterpoises 53 such aswashers, which may be secured in place by a nut 54. These counterpoises53 make it possible to secure a delicate balance.

It will be understood that four complete vane mechanisms are provided,which are identical in all respects except that they are located at fourpositions, spaced evenly around the fairing 13. Two .of these are shownin Fig. 2, the one at the left being in front elevation, whereas theother one is in central sectional side elevation, so that these twoviews jointly give complete details of the structures involved. In orderto avoid interference between the two shafts 21, which cross at rightangles at the axis of the rocket, obviously these shafts must be atslightly different levels, as indicated in Fig. 2, where the shaft 21shown in end-section is high enough to pass above the one shown in sideelevation, at the right of the same figure.

It should be understood that while the preferred form of the inventionis shown in Figs. land 2, modifications .in the inner vane structuresare also contemplated, as shown in Figs. 4, 5, 8 and 9.

In Figs. 4 and 5 are shown sections mutually at right angles, of vanestructures designedto make it possible to mount both the cross-shafts 21at the same level. This is accomplished by making one vane 55 extend theentire width of the outlet of nozzle 12, but with a notch 56 cut in themiddle of its upper half, this notch serving to allow the shaft 21, thatcarries the companion vane 57, to pass freely across and through theupper part of vane 55. The vane 57 in turn has a notch 58 cut in itslower part, to permit the lower middle part of vane 55 to cross freely.In this way these two vanes can operate without mutual interference, andwith all the shafts 21 at the same level.

The structure diagrammatically shown in Figs. 6 and 7 is that alreadydiscussed and illustrated in detail in Figs. l and 2, and is repeatedhere for ready comparison. It differs from the Figs. 4 and 5 form inthat each shaft carries two entirely distinct vanes, and in that theshafts are not at the same level, so that clearance is providedautomatically.

Finally, the Figs. 8 and 9 form shows a third type, wherein all theshafts are at the same level, but unlike the preceding types, each vanehas its own shaft, which stops short of the location at which all theshafts would intersect. Here the through shafts 21 are replaced by theshorter shafts 59, which are all alike, each carrying a similar vane 60.It will be understood that regardless of which type of vane structure ischosen, the remainder of the operating mechanism will be as shown indetail in Figs. 1 and 2. Possibly the long shafts 21, that extendentirely across the rocket, have certain advantages of rigidity,inasmuch as they are pivotally mounted at both ends, but against this isto be considered the fact that the central portions of the crossedshafts, extending between the vanes, form unnecessary obstructions tothe rocket jet, and moreover may become highly heated and perhaps warpedthereby, with the possibility of jamming.

The operation of the device will be evident from the structuredisclosed. Briefly, whenever the rocket follows a course that is not inline with its own axis, there will be an angle of attack of the externalair on the outer vanes 36, which will cause them to turn the respectiveshaft, or shafts 37.

This, through the linkage 28, 39, will cause an opposite rotation of theinner vanes 20, the latter in turn deflecting the gases emanating fromthe mouth 12 of the rocket.

i The resulting reactions will tend to return the rocket to its properorientation.

While the form of the invention at present preferred has been disclosedin detail, and several modifications have been described or suggested,it is to be understood that numerous other embodiments are possible.Therefore, the present invention is not limited to the specific featuresdisclosed, but is defined solely in and by the following claims.

I claim:

1. In an aerial missile having a propelling jet, a jet vane pivotallymounted in the jet orifice, a trailing vane pivotally mounted on saidvehicle and exposed to the medium through which the vehicle moves, saidtrailing vane being arranged to trail rearwardly of said pivot line, andmeans mechanically connecting said trailing vane to said jet vane sothat said trailing vane controls said jet vane in contra direction tothe direction of movement of said trailing vane, whereby whenever saidtrailing vane is deflected by said medium because the axis of saidvehicle does not coincide with its direction of motion, a correspondingcontra movement of said jet vane will occur, said jet vane, in turn,deflecting said jet such that the deflecting jet will tend to returnsaid vehicle to its proper orientation.

2. In an aerial missile having a propelling jet, a jet vane pivotallymounted in the jet orifice, a trailing vane pivotally mounted on saidvehicle and exposed to the medium through which the vehicle moves, saidtrailing vane being arranged to trail rearwardly of said pivot line, andlinkage means connecting said trailing vane to said jet vane so thatsaid trailing vane controls said jet vane in a contra direction to thedirection of movement of said trailing vane, whereby whenever saidtrailing vane is deflected by said medium because the axis of saidvehicle does not coincide with its direction of motion, a correspondingcontra movement of said jet vane will occur, said jet vane, in turn,deflecting said jet such that the deflecting jet will tend to returnsaid vehicle to its proper orientation.

3. In an aerial missile having a propelling jet, two jet vanes pivotallymounted on separate shafts in the jet orifice, for controlling the jetin at least two directions, said jet vanes being movable about axessubstantially at right angles to each other, trailing vanes,corresponding to said jet vanes, pivotally mounted on said vehicle andexposed to the medium through which the vehicle moves, said trailingvanes being arranged to trail rearwardly of said respective pivot lines,and means mechanically connecting said trailing vanes to said jet vanesso that said trailing vanes control said jet vanes in contra directionsto the directions of movement of said trailing vanes, whereby wheneversaid trailing vanes are deflected by said medium because the axis ofsaid vehicle does not coincide with its direction of motion,corresponding contra movements of said jet vanes will occur, said jetvanes, in turn, will deflect said jet such that the deflecting jet willtend to return said vehicle to its proper orientation.

4. An arrangement as set forth in claim 3, wherein said jet vane shaftsare located in the same plane transverse to the longitudinal axis ofsaid vehicle.

5. An arrangement as set forth in claim 3, wherein said jet vane shaftsare located in parallel planes transverse to the longitudinal axis ofsaid vehicle.

6. An arrangement as set forth in claim 3, wherein said jet vanes extendthroughout the width of. said jet orifice.

References Cited in the file of this patent UNITED STATES PATENTS502,168 Battey July 25, 1893 1,083,464 Roche Jan. 6, 1914 1,879,187Goddard Sept. 27, 1932 2,419,866 Wilson Apr. 29, 1947

